Apparatus and method for testing liquid propelled rocket

ABSTRACT

Disclosed is an apparatus for testing a water rocket and a method for use thereof, the apparatus comprising a housing, a load cell assembly, a launcher assembly, a rocket assembly, and a base piston. The load cell assembly, the launcher assembly, the rocket assembly, and base piston all situated within the housing. A hose running from the exterior of the housing to the launcher assembly and/or the rocket assembly, whereby water or air may be supplied to the launcher assembly or the rocket assembly. The supply of air and/or water pressurizes the rocket assembly and the launcher assembly, which may then be released to cause the rocket to exert a force in a direction opposite to the direction of the release of water and air. The load cell is adapted to capture and record the thrust of the water rocket. The housing is adapted to retain the released water within the housing. The base piston is adapted to move the launcher assembly out of the way of the releasing water and air, whereby the launcher assembly does not impede the exit of the water or air that could result in inaccurate data.

CLAIM OF PRIORITY

This application is being filed as a non-provisional patent applicationunder 35 U.S.C. § 111(a) and 37 CFR § 1.53(b). This application claimspriority under 35 U.S.C. § 119(e) to U.S. provisional patent applicationSer. No. 62/991,177 filed on Mar. 18, 2020, the contents of which areincorporated herein by reference.

FIELD OF INVENTION

The invention relates generally to devices, such as liquid propelledrockets, used to teach principles of the operation of rockets. Inparticular, the present invention is directed to an apparatus fortesting the performance of liquid propelled rockets, such as waterrockets, and methods for using the same.

BACKGROUND OF THE INVENTION

Liquid propelled rockets, and more specifically water rockets, arecommonly used to demonstrate and learn about the principles of rocketengines and Newton's third law of motion. They provide a safe and funway to replicate the launch of a rocket using simple, inexpensivecomponents. These types of rockets can be used by teachers and educatorsto demonstrate the laws of physics and their flight paths can be relatedback to specific mathematical equations. Thus, water rockets are auseful tool in teaching science, as well as gaining students' interestin the study of physics and mathematics.

However, due to the chaotic nature of such rockets' flight paths, it isdifficult to measure and record data from the launch of the rockets,such as the rocket's thrust over the course of its flight. Further, theexpulsion of water from the rocket during launch makes any attempt atlaunching a rocket indoor and recording this flight data extremelydifficult. The present disclosure overcomes these inherent flaws byproviding an apparatus and method for testing water rocket enginesindoors and accurately recording data from the launch of the rocket.Additional details of the present invention are discussed below.

SUMMARY OF THE INVENTION

Small rockets, particularly water rockets, are a teaching tool commonlyused in a variety of subjects in the STEM (science, technology,engineering, and mathematics) curriculum. By studying the performanceand principles behind water rockets, teachers can craft courseworkrelevant to a large set of STEM subjects. For example, students canlearn and document their abilities with the following concepts: inertia,gravity, air resistance, Newton's laws of motion, acceleration,relationships between work and energy or impulse and momentum,projectile motion, freefall calculations, and internal and externalballistics, not to mention the practice of true engineering and thescientific method.

Water rockets provide a safe and engaging way to replicate the launch ofa rocket using simple, inexpensive components. In sum, water rockets area useful tool in teaching science, as well as developing students'interest in the study of physics, engineering, and mathematics.

In teaching students about the principles behind water rockets, it iscommon to use a variety of tools and sensors to record for lateranalysis several performance parameters during flight cycle of therocket. For example, it is often useful to record, in real-time, thethrust generated by the rocket from the moment of launch until the endof powered flight. However, due to the chaotic and fast-paced nature ofa water rocket launch, and the often-great distances traveled by waterrockets, field testing is generally very difficult and inaccurate.

Accordingly, it has been very difficult to easily and inexpensivelymeasure and record data from the launch of water rockets, such as therocket's thrust over the course of its flight. Further, the expulsion ofwater from the rocket during launch makes any attempt at launching arocket indoor and recording this flight data extremely difficult. Thepresent disclosure overcomes these inherent flaws by providing anapparatus and method for testing water rocket engines indoors andaccurately recording data from the launch of the rocket.

The disclosed apparatus comprises the following components: a housing, aload cell assembly, a launcher assembly, a rocket assembly, and a basepiston. The load cell assembly, the launcher assembly, the rocketassembly, and base piston are all situated within the housing. A hosemay run from the exterior of the housing to the launcher assembly and/orthe rocket assembly, whereby water or air may be supplied to thelauncher assembly or the rocket assembly. The supply of air and/or waterpressurizes the rocket assembly and the launcher assembly, which maythen be released to cause the rocket to exert a force in a directionopposite to the direction of the release of water and air. The load cellis adapted to capture and record the thrust of the water rocket. Thehousing is adapted to retain the released water within the housing. Thebase piston is adapted to move the launcher assembly out of the way ofthe releasing water and air, whereby the launcher assembly does notimpede the exit of the water or air that could result in inaccuratedata.

The method herein disclosed comprises the following steps: filling therocket assembly with the desired amount of water; loading the rocketassembly onto the launcher assembly; raising the rocket assembly to theload cell assembly; arming the launcher assembly and locking the rocketassembly in place; adjusting the load cell assembly to ensure that theload cell assembly is at an optimal distance from the top of the rocketassembly (in some embodiments approximately 25 mm); pressurizing therocket assembly to the desired gas pressure; conducting a furtheradjustment of the distance between the load cell assembly and the top ofthe rocket assembly; triggering the release of the rocket assembly;moving the launcher assembly away from the ejecting water and air; andrecording the data from the thrust of the rocket upon the load cellassembly. During the launch, the rocket assembly maintains contact withthe load cell throughout the thrust phase to avoid losing any thrustdata. Periods of lost contact during thrust phase results in loss ofrecorded data.

Additional details regarding the operation of the disclosed apparatusand method are included in the following description which includesnon-limiting embodiments of certain aspects of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is an external illustration of the housing in one embodiment ofthe present invention.

FIG. 2 is an illustration showing the fitment of the water rockettesting apparatus of the present invention within the housing.

FIG. 3 is a frontal view of the water rocket testing apparatus of thepresent invention with the housing not shown for clarity.

FIG. 4 is a side view of the water rocket testing apparatus of thepresent invention with the housing not shown for clarity.

FIG. 5 is a perspective view of the water rocket testing apparatus ofthe present invention with the housing not shown for clarity.

FIG. 6 is an external illustration of the load cell assembly of thepresent invention and its various components.

FIGS. 7A-7K, illustrate the sequence of launch and flight of a waterrocket being tested in an apparatus according to the present invention.

DETAILED DESCRIPTION OF THE INVENTION

Apparatus

The present specification discloses an apparatus and method for testinga water rocket and the recording of operational data from the simulatedpowered flight of the water rocket. The major components of theapparatus comprise a housing, a load cell assembly, a launcher assembly,a rocket assembly, and a base piston. In some embodiments, the apparatusmay further comprise one or more circuit boards, and one or morepneumatic controllers, such as solenoid motors and/or flow regulators,to control the actuation and timing of various components of theapparatus.

Referring first to FIG. 1, shown is an exterior view of the housing(100). FIG. 2 illustrates the various other main components locatedwithin the housing, with the door (101) of the housing removed forpurposes of visibility of interior components. The housing is adapted tohouse the other main components of the apparatus, including the loadcell assembly (300), the launcher assembly (400), the rocket assembly(200), and the base piston (500). The housing is further adapted toretain the rocket assembly (200) within its interior upon launch of therocket assembly, as well as any water ejected from the rocket assemblyduring the launch, which will eventually exit the housing through adrain (106).

In the shown embodiment, the housing (100) comprises a rectangularcabinet comprised of multiple frame members (105) and wall members(104). However, the housing (100) may have virtually any shape,including cylindrical, prismatic, or any other shape suitable to housethe required components. The wall members may completely envelop theexterior of the housing (100) or there may be portions of the exterior(103) which are devoid of wall members and may vent the interior of thehousing (100) to the exterior. Wall members (104) may be opaque, or in apreferable embodiment they may be transparent to permit visibility ofthe interior components. The wall members (104) may also be acombination of opaque and transparent components.

The housing (100) may also be closed at a top end and a bottom end orthe top end and the bottom end may be left substantially open. In oneembodiment, the bottom end of the housings comprises a drain (106),whereby water expelled from the rocket assembly may be drained from theapparatus. Additionally, a plurality of legs (102) may be provided topermit the bottom of the housing (100) to be elevated above the groundto permit full evacuation of water through the drain (106).

The housing may also comprise a door (101) on one of its walls, wherebythe interior of the housing may be accessed through its opening. Thedoor (101) may further comprise a safety switch (not shown), whereby theapparatus will not function while the door is in an open position. Thesafety switch may be a mechanical, electrical, or magnetic switch thatphysically or electrically impedes the launch of the rocket assembly orthe pressurization of the rocket assembly or the launcher assembly.

The housing provides support for the load cell assembly (300) and thelauncher assembly (400), whereby the load cell assembly (300) and thelauncher assembly (400) are temporarily or permanently attached to thehousing (100).

Referring next to FIGS. 3, 4 and 5, the rocket assembly (200) maycomprise a pressure vessel (or bottle) (201) and a nozzle (202). Thepressure vessel (201) is typically a polyethylene terephthalate (PET)bottle, such as a carbonated soft drink bottle. However, the pressurevessel may comprise any material and configuration, if it issubstantially water-tight, airtight, and has only a single, relativelynarrow, opening for a nozzle (202). The nozzle (202) of the rocketassembly (200) may be a separate component from the pressure vessel(201), or the pressure vessel (201) may be integrated with the nozzle(202). The rocket assembly may further comprise fins, a nose cone, orother stabilizers (not shown).

Prior to launch of the rocket assembly, a liquid, which acts as thepropellant, is introduced into the pressure vessel (201). The liquid maybe added prior to the rocket assembly (200) being placed within thehousing (100) or it may be added while situated within the housing (100)via a hose (405) in the launcher assembly (400). The amount of liquidused may vary depending on the parameters of the test and the design ofthe experiment. The liquid is typically water, but any other liquid maybe used within the pressure vessel. The pressure vessel is also adaptedto hold pressurized gas in addition to the liquid, which may similarlybe introduced into the pressure vessel via hose (405) or via a separatehose. The gas may be air, or any other substantially compressible gasthat is less dense than the liquid. As additional gas is introduced andforced into the pressure vessel, (200), the gas compresses andpressurizes. The amount and final pressure of the of gas may varydepending on the parameters of the test and the design of theexperiment.

When the apparatus is in a fully assembled position, the nozzle (202) ofthe rocket assembly (200) is situated at a bottom end of the rocketassembly and below the pressure vessel (201). Due to gravity, and thedensity of the liquid being greater than that of the pressurized gas,the liquid within the pressure vessel migrates down proximate thenozzle. The gas, in turn, migrates to the top of the pressure vessel(201). Gas may be continually introduced into the pressure vessel (201)until the desired gas pressure is reached and additional gas maythereafter be introduced, or gas may be removed, if the pressure changesprior to launch. A manual purge valve (not shown) for removal of gasfrom the pressure vessel (201) may also be present in some embodimentsto safely depressurize the pressure vessel (201) in the event of a powerfailure.

The rocket assembly (200) sits atop the launcher mechanism (400) Thenozzle (202) is covered by the trigger mechanism (401) of the launcherassembly (400). The trigger mechanism (401) may comprise a valve,stopper, or gate which, when open or withdrawn, permits liquid to escapethe pressure vessel (200) because of pressure exerted by the gas.

During a launch of the rocket assembly, the pressurized gas forcesliquid to escape the pressure vessel (201) via the nozzle (202). Inaccordance with Newton's third law of motion, the force of the escapingliquid downward through the nozzle creates thrust in the opposite,upward direction. Water rocket engine tests can only be conducted insituations where the liquid is closer to the source of gravity, so thatthe compressed gases push the liquids out, and, in accordance with thelaw of conservation of momentum, the ejected liquid imparts momentum tothe rocket.

In one embodiment, the trigger mechanism (401) is adapted to clamp therocket assembly (200) in place during pressurization of the rocketassembly and impede the pressurized air and fluid in the pressure vessel(201) from escaping through the nozzle (202) prior to the launch of therocket assembly. The trigger mechanism (401) may be activated to allowrelease of the pressurized air and liquid within the pressure vessel(201) through the nozzle (202), causing the launch of the rocketassembly. The trigger mechanism (401) may be activated through thedeployment of a pneumatic or hydraulic piston. Alternatively, thetrigger mechanism may be controlled using an electrical signal capableof locking and releasing the trigger mechanism. Other means, such as amanual mechanical release, may be used to operate the trigger mechanism(401).

The launcher assembly (400) may further comprise an adapter orconnecting element adapted to attach attaching the trigger mechanism toa base piston (500). One purpose of the base piston (500) is to separatethe trigger mechanism (401) from the nozzle (201), as quickly aspossible upon launch so that the launcher assembly (400), andparticularly the trigger mechanism (401) does not interfere with theperformance of the rocket assembly (200).

In one embodiment, the adapter comprises a face plate (404) adapted toreside within a vertical slot (501) of the base piston (500). Thisconfiguration aids in the proper positioning of the launcher assemblyand the rocket assembly relative to the housing (100) and the load cellassembly (300). The face plate (404) may be removably attached to thevertical slot (501), thereby allowing for the movement of the basepiston (500) to effect a corresponding movement of the launcher assembly(400).

In one embodiment, the face plate (404) and the vertical slot (501) areattached by a rod or lock residing in mating holes of the face plate(404) and the vertical slot (501). In another embodiment, the verticalslot (501) may be clamped down onto the face plate (404). Althoughdisclosed as using a face plate and vertical slot, the launcher assemblyand the base piston may be attached by any method known in the art forattaching separate components. Alternatively, the base piston and thelauncher assembly may be a single, integral component. Although thelauncher assembly is disclosed as featuring the above components, anyconfiguration of a launcher assembly known in the art may be used fortriggering the launch of the rocket assembly (200).

The base piston (501) may serve two purposes. The first is to raise therocket assembly up to the load cell assembly (300) prior to launch, sothat the upper end of the pressure vessel (201) (or an attached nosecone) is in direct contact with, or near, the load cell assembly (300)at the time of launch. This allows for an accurate and smooth reading ofthe thrust of the rocket assembly during simulated flight. If the upperend of the pressure vessel (201) were not in contact with the load cellassembly (300) at the time of launch, there is a significant risk thatduring launch, the sudden violent impact of the pressure vessel (201)with the load cell assembly (300) could cause damage to the apparatusand/or result in inaccurate readings. This arrangement also allows for avariety of water rocket engines to be used of various volumes andshapes.

The second purpose, which was previously mentioned, is to quickly movethe launcher assembly (400) away from the rocket assembly (200) uponlaunch. Upon the activation of the trigger mechanism (401), which inturn triggers the launch of the rocket assembly (200), the base piston(500) is simultaneously, or nearly simultaneously, triggered to actuatedownward, thereby moving the launcher assembly (400) away from therocket assembly (200) and the liquid and gas expelling from the nozzle(202) of the rocket assembly (200). The launcher assembly (400) is movedaway from the rocket assembly (200) upon launch because a portion of thethrust may impinge upon by the launcher assembly (400) during theexpulsion of the liquid and gas, causing “back pressure” an inaccuratemeasurement of the thrust of the rocket assembly (200).

Although the illustrated embodiments show the base piston (500) belowthe launcher assembly (400) and actuating downward to move the launcherassembly (400), a lateral, curvilinear, or other type of movement of thelauncher assembly (400) away from the ejecting liquid and gas of therocket assembly (200) is within the scope of this disclosure. The basepiston (500) may be affixed within the housing (100) or may be aseparate component. Other methods may also be used to separate thelauncher assembly (400) from the rocket assembly (200) during launch,these include having the trigger mechanism (401) be a free-standingcomponent that is secured only to the nozzle (202) just prior to launchand is ejected away from the nozzle (202) by a combination of gravityand the force of the liquid expelled from the rocket assembly (200) uponlaunch.

In one embodiment of the disclosure, the trigger mechanism (401) furthercomprises a piston that is pressurized prior to the pressurization ofthe pressure vessel (201). Upon release of pressure within the piston,the trigger mechanism (401) releases the rocket assembly (200),initiating its launch. The piston of the trigger mechanism (401) and thebase piston (500) may be controlled by a single actuator.

In another embodiment of the disclosure the piston of the triggeringmechanism (401) and the base piston (500) may be controlled by twoactuators, allowing for the fine tuning of the timing of the launch andmovement of the launcher assembly (400). In an alternative embodiment,the launch of the rocket assembly (200) and downward movement of thelauncher assembly (400) occur nearly simultaneously. This allows for therocket assembly (200) to remain in contact with the load cell assembly(300) at all time, while also allowing the expelling water and air toexit the nozzle (202) unimpeded, thereby removing anomalies in any datarecordation.

In some embodiments, the base piston (500) may be connected to a flowregulator (not shown) which can slow down the rate of movement of thebase piston (500) in one direction, while allowing for a faster rate ofmovement in the other direction. For example, a flow regulator may beused to slow down the speed of movement of the base piston (500) in theupward direction, when the top of the rocket assembly (200) is beingpositioned in close proximity to the load cell assembly (300), whilepermitting the base piston to move faster in the opposite direction,when the base piston (500) is used to separate the launcher assembly(400) from the rocket assembly (200) during launch.

In some embodiments, the apparatus may further include visual indicia,such as an LED light, or an array of LED lights, to indicate the launchstage. In addition, a countdown timer display may also be incorporatedas well as displays showing other parameters, such as gas pressure andthrust, in real time.

Referring next to FIG. 6, shown is a detailed view of the load cellassembly (300). The load cell assembly (300) is situated above the upperend of the rocket assembly (200). The load cell assembly (300) isadapted to read and record the thrust generated by the rocket assembly(200) throughout its simulated flight. In one embodiment of the loadcell assembly (300), the load cell assembly (300) comprises contactplate (302), a ball (304), a load cell transducer (306), a housing (303)(shown transparent for clarity) and a support plate (301). The contactplate (302) is situated at a bottom end of the load cell assembly (300)and is adapted to remain in contact with the rocket assembly (200)throughout its launch. The contact plate is supported by spring-loadedscrews (305), which are in turn connected to the support plate (301).The spring-loaded screws (305) ensure that the top surface of thecontact plate (302) is in continuous contact with a bottom end of theball (304) and that the contact plate (302) can further move upward togenerate a greater force onto the ball (304). The top end of the ball isin direct contact with load cell transducer (306) which is adapted togenerate an electrical signal proportional to the force generated by theball (304) upon the load cell transducer (306).

The load cell transducer (306) is in turn attached to the support plate(301). In one embodiment, ball (304) is a spherical metallic ball, andthe contact and support plates are comprised of carbon fiber. The ball(304) may also be housed within a ball housing, whereby the location ofthe ball (304) may be fixed relative to the contact plate and supportplate. In an alternative embodiment (not shown), the ball (304) may bereplaced by a differently shaped component, such as a rod or a bell,which can directly transfer pressure from the contact plate (302) to theload cell transducer (306).

The configuration of the load cell assembly (300) allows for the forcegenerated by the launch of the rocket to translate from the contactplate (302) to the ball (304) and then unto the load cell transducer(306), with minimal loss of energy. Although disclosed as a sphericalball, the ball (304) may be any shape that allows the force upon thecontact plate (302) to be concentrated to a small area and thentransmitted to the load cell transducer (306) for reading andrecordation of the force.

In some embodiments, the load cell assembly (300) may be adapted totravel up and down vertically within the housing (100), independent ofthe other components. This allows for the contact plate (302) to contactthe upper end of the rocket assembly (200) regardless of the size of thepressure vessel (201). The load cell assembly (300) may be raised andlowered by an actuator mechanism (310, FIG. 4) using one or morevertical, linear rods. Like the base piston (500), this arrangement alsoallows for a variety of water rocket engines to be used of variousvolumes and shapes.

The apparatus may further comprise other features, such as temperaturesensors and a time-of-flight sensor. The temperature sensors may readand record the temperatures within the housing, outside the housing, andwithin the pressure vessel (201). The time-of-flight sensor is a rangeimaging camera system that is capable of recording distance between thesensor and a target subject for each point of the image. This may allowfor a user of the apparatus to measure the expansion of the pressurevessel (201) before and during launch, assisting in the analysis of themechanical dynamics of the rocket assembly (200). Further, the userwould be able to log any changes in the dimensions of the pressurevessel (201) after each launch of the rocket assembly (200). Therecorded data prior to and during the launch of the rocket assembly(200) may be processed, using computer instructions and mathematicalequations, to create graphs or tables detailing this information. Theinformation may also be used to predict certain aspects of launch, suchas flight path and maximum height of the launch.

Method of Use

As disclosed above, the method of launching the water rocket within thefully assembled apparatus and recording the launch is, in an exemplaryembodiment, as follows: attaching the rocket assembly (200) to thelauncher assembly (400); attaching the launcher assembly (400) to thebase piston (500) (if not previously attached); adding liquid to thepressure vessel (201) of the rocket assembly (200) (if not added priorto the attachment to the launcher assembly (400)); arming of thelauncher assembly (400) by pressurization of an internal piston or useof an electrical signal, which locks the rocket assembly (200) in place;pressurization of the base piston (500), thereby raising the launcherassembly (400) and rocket assembly (200) to a position where the top ofthe rocket assembly (200) is in near proximity to the contact plate(302) of the load cell assembly (300); pressurization of the gas insidethe pressure vessel (201) (including monitoring for pressure changes andadding or removing gas as necessary throughout the launch); lowering theload cell assembly (300), and/or further raising the launcher assembly(400) (as necessary) in order to ensure pre-launch contact between theupper end of the rocket assembly (200) and the contact plate (302) ofthe load cell assembly (300); simultaneously, or nearly simultaneously,activating the trigger mechanism (401) and thus opening the nozzle (202)whereby the pressurized gas within the pressure vessel (201) forces theliquid to exit through the nozzle (202) of the rocket assembly (200)generating thrust; activating the base piston (500), whereby the entirelauncher assembly (400) is moved away from the liquid and air exitingthrough the nozzle (202) of the rocket assembly (200); and recordingdata prior to and throughout the simulated flight of the rocket assembly(200). This data may be further processed using computers andmathematical equations to generate charts, graphs, and/or tablesdetailing the launch information.

Referring to FIGS. 7A-7K, shown are photographs illustrating a typicallaunch sequence using the apparatus and method disclosed herein. FIG. 7Ashows the apparatus prior to launch with the base piston (500) at itslowest position. In FIG. 7B, the base piston (500) is being raised sothat pressure vessel (201) approaches the contact plate (302) of theload cell assembly (300). In FIG. 7C, the base piston (500) is fullyraised with pressure vessel (201) near contact plate (302) of the loadcell assembly (300). In FIG. 7D, the load cell assembly (300) has begunto move down and the contact plate is approaching the top of thepressure vessel (201). In FIG. 7E, the contact plate (302) of the loadcell assembly (300) has just contacted the top of the pressure vessel(201) and the pressure vessel (201) has begun to be pressurized byadding gas. At this point, the load cell assembly (300) or rocketassembly (200) may optionally pull back up slightly to account for anychange in the shape of the pressure vessel (201) due to pressurization.In FIG. 7F the pressure vessel (201) is at its final desired pressure,and the load cell assembly (300) is in its final launch positioncontacting the pressure vessel (201). However, if a pressure change isdetected, and/or a separation develops between the contact plate (302)and the top of the pressure vessel (201), additional adjustments to thepressure and to the position of the contact plate can be made,automatically or manually, until launch. In FIG. 7G, the triggermechanism (401) has just released the nozzle (202) and the nozzle (202)has been placed in the open position. In FIG. 7H, liquid is beginning toemerge from the nozzle (201) and the base piston (500), and launcherassembly (400) have begun to move downward and away from the rocketassembly (200). In FIG. 7I, the base piston (500) and launcher assembly(400) are in their lowest position and the launch is in full progress.Note that the rate of movement of the base piston (500) in FIGS. 7H and7I is faster than the rate of movement in FIG. 7B due to the use of aflow regulator. In FIG. 7J, the gas pressure inside the pressure vessel(201) is nearly exhausted and the pressure vessel (201) has begun tofall away from the load cell assembly (300). Finally, in FIG. 7K, thelaunch sequence and the powered portion of the simulated flight arecompleted. It should be noted that thrust data may be collected from theload cell transducer throughout the entire launch sequence.

Although described above in connection with certain specific components,these descriptions are not intended to be limiting as variousmodifications may be made therein without departing from the spirit ofthe invention and within the scope and range of equivalent of thedescribed embodiments. Encompassed embodiments of the present inventioncan be used in all applications where the testing of rockets of anytype, or even other propulsion devices is desired or beneficial.

1. An apparatus for testing a liquid propelled rocket comprising: a loadcell assembly having a contact plate and a load cell transducer, thecontact plate configured to transfer a force applied to the contactplate to the load cell transducer, the load cell transducer adapted togenerate an electrical signal proportional to the force transferred tothe load cell transducer by the contact plate; a rocket assembly havinga top surface, a pressure vessel, and a nozzle, the nozzle beingoperable between a closed and an open position, the pressure vesselbeing adapted to receive a liquid and a gas and to maintain the liquidand gas combination under greater than atmospheric pressure when thenozzle is in the closed position; a launcher assembly having a triggermechanism, the trigger mechanism adapted to receive the nozzle andconfigured to operate the nozzle between the open and closed positions,the trigger mechanism further adapted to engage with the nozzle when thenozzle is in the closed position, and to release the nozzle when thenozzle is in the open position; a base piston, the base piston attachedto the trigger mechanism and configured to separate the triggermechanism from the nozzle upon operation of the nozzle from the closedposition to the open position; wherein, in a launch position, the rocketassembly is located below the load cell assembly, the nozzle is in theclosed position and pointed in a downward direction, and the triggermechanism is engaged with the nozzle; and wherein at least one of theload cell assembly, and the engaged rocket assembly and launcherassembly, are moveable in the vertical direction to cause the contactplate of the load cell assembly and the top surface of the rocketassembly to come into contact.
 2. (canceled)
 3. The apparatus of claim1, wherein the base piston is further configured to move the engagedrocket assembly and launcher assembly in the direction of the load cellassembly.
 4. The apparatus of claim 3, wherein the rate of movement ofthe base piston in the direction of the load cell assembly is lower thanthe rate of movement of the base piston when the base piston separatesthe trigger mechanism from the nozzle.
 5. The apparatus of claim 1further comprising a housing, the housing adapted to contain the loadcell assembly, the rocket assembly, and the launcher assembly.
 6. Theapparatus of claim 5, wherein the housing further comprises a door, thedoor operable between an open position and a closed position.
 7. Theapparatus of claim 5, wherein the housing further comprises a lowersurface and a drain located in the lower surface, the drain configuredto permit liquid to flow from inside the housing to outside the housing.8. (canceled)
 9. (canceled)
 10. (canceled)
 11. (canceled)
 12. A methodfor testing a liquid propelled rocket comprising the steps of: providinga load cell assembly having a contact plate and a load cell transducer,the contact plate configured to transfer a force applied to the contactplate to the load cell transducer, the load cell transducer adapted togenerate an electrical signal proportional to the force transferred tothe load cell transducer by the contact plate; providing a rocketassembly having a top surface, a pressure vessel, and a nozzle, thenozzle being operable between a closed and an open position, thepressure vessel being adapted to receive a liquid and a gas and tomaintain the liquid and gas combination under greater than atmosphericpressure when the nozzle is in the closed position; providing a launcherassembly having a trigger mechanism, the trigger mechanism adapted toreceive the nozzle and configured to operate the nozzle between the openand closed positions, the trigger mechanism further adapted to engagewith the nozzle when the nozzle is in the closed position, and torelease the nozzle when the nozzle is in the open position; providing abase piston, the base piston attached to the trigger mechanism andconfigured to separate the trigger mechanism from the nozzle uponoperation of the nozzle from the closed position to the open position;wherein, in a launch position, the rocket assembly is located below theload cell assembly, the nozzle is in the closed position and pointed ina downward direction, and the trigger mechanism is engaged with thenozzle; and wherein at least one of the load cell assembly, and theengaged rocket assembly and launcher assembly, are moveable in thevertical direction to cause the contact plate of the load cell assemblyand the top surface of the rocket assembly to come into contact;engaging the trigger mechanism with the nozzle with the nozzle in theopen position; injecting an amount of liquid into the pressure vessel;injecting an amount of gas into the pressure vessel sufficient to createa higher than atmospheric pressure inside the pressure vessel; operatingthe nozzle to the closed position; moving the engaged rocket assemblyand launcher assembly in the vertical direction until the contact plateof the load cell assembly and the top surface of the rocket assemblycome into contact; operating the nozzle into the open position; andrecording the electrical signal generated by the load cell transducer.13. The method of claim 12, wherein the base piston is furtherconfigured to move the engaged rocket assembly and launcher assembly inthe direction of the load cell assembly.
 14. The method of claim 13,wherein the rate of movement of the base piston in the direction of theload cell assembly is lower than the rate of movement of the base pistonwhen the base piston separates the trigger mechanism from the nozzle.